TITLE DH1_INLAUNCH.ASC: DH-1 Launch
MODULES
 G2   ENVIRONMENT
 A2   PROPULSION
 A1   AERODYNAMICS
 A3   FORCES
 D1   NEWTONS LAW
END
OPTMET = 1.0000    ! E Units of measure 1 = metric; 0 = English
OPNORO = 1.00000   ! E Option flag: 0=rotating earth model; 1=Non-rotating e
! *** PROPULSION *
MPROP = INT(2)     ! D/G =0:No thrust; =1:Coasting =2:Burning
FUELI = 31818.0    ! D Initial total fuel in stage - kg
FUELR = 482.0      ! D Maximum fuel rate through motor - kg/s
SPI = 353.00       ! D Effective specific impulse - s
AEXIT = 4.86       ! D Nozzle exit aerea - m^2
THRTL = 1.0000     ! D Throttle (0-1) - ND
PEXIT = 101325.0
! *** VEHICLE DATA
MAERO = INT(11)    ! D =|MAERT|MAERV|, MAERT=1:Type, MAERV:Stage #
SREF = 10.000      ! D Aerodynamic reference area - m^2
VMASSI = 95000.0   ! D Initial mass of remaining stages - kg
PHIMVX = 0.000     ! D Bank angle of maneuver plane wrt vertical - deg
THTVGX = 90.000    ! I Flight path angle from horizontal - deg
PSIVGX = 0.000     ! I Heading angle from north - deg
! *** LAUNCH CONDI
BLON = 4.8770      ! I/G Vehicle longitude - rad
BLAT = 0.49620     ! I/G Vehicle latitude - rad
BALT = 1.0000      ! I/O Vehicle altitude = m
DVBE = 1.0000      ! I/G Geographic speed - m/s
! *** PRINTING
PPP = 0.50000      ! E Time interval writing to TRAJ.BIN or TRAJ.ASC - sec
CPP = 5.0000       ! E Time interval writing to Screen or TABOUT.ASC - sec
DER = 0.01000      ! E Integration interval - sec
IF FUEL < 3182.0   ! G Fuel remaining in stage - kg
FUELR = 89.68      ! D Maximum fuel rate through motor - kg/s
AEXIT = 4.29       ! D Nozzle exit aerea - m^2
! ##1 MECO##
IF FUEL < 0.       ! G Fuel remaining in stage - kg
VMASSI = 18182.0   ! D Initial mass of remaining stages - kg
FUELI = 0          ! D Initial total fuel in stage - kg
MPROP = INT(0)     ! D/G =0:No thrust; =1:Coasting =2:Burning
IF BALT < 1000     ! E  Trajectory time - s
RUN
STOP
